GOE 256 (JUNKERS E) AIRFOIL (goe256-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 256 (JUNKERS E) AIRFOIL (goe256-il) Reynolds number: 200,000 Max Cl/Cd: 69.58 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe256-il-200000.txt Download as CSV file: xf-goe256-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 256 (JUNKERS E) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1399 0.09838 0.09459 -0.0892 0.9690 0.0781
-9.750 -0.1306 0.09471 0.09091 -0.0926 0.9626 0.0804
-9.500 -0.1621 0.08419 0.08041 -0.1116 0.9531 0.0841
-9.250 -0.1376 0.08250 0.07871 -0.1081 0.9491 0.0848
-9.000 -0.1164 0.08035 0.07655 -0.1077 0.9447 0.0857
-8.750 -0.0983 0.07770 0.07388 -0.1092 0.9405 0.0871
-8.500 -0.0916 0.07495 0.07112 -0.1106 0.9325 0.0891
-8.250 -0.1015 0.06956 0.06570 -0.1177 0.9231 0.0928
-8.000 -0.1622 0.06106 0.05684 -0.1238 0.9071 0.0960
-7.750 -0.1381 0.05928 0.05516 -0.1230 0.9037 0.0970
-7.500 -0.1272 0.05784 0.05374 -0.1216 0.8967 0.0982
-7.250 -0.1157 0.05577 0.05162 -0.1213 0.8918 0.0999
-7.000 -0.1076 0.05291 0.04861 -0.1217 0.8877 0.1034
-6.750 -0.1310 0.04895 0.04417 -0.1195 0.8770 0.1096
-6.500 -0.1101 0.04687 0.04214 -0.1194 0.8735 0.1110
-6.250 -0.1303 0.03721 0.03129 -0.1146 0.8664 0.0824
-6.000 -0.1193 0.03492 0.02882 -0.1124 0.8597 0.0811
-5.750 -0.1017 0.03196 0.02548 -0.1111 0.8553 0.0793
-5.500 -0.0787 0.02935 0.02246 -0.1102 0.8520 0.0786
-5.250 -0.0672 0.02815 0.02102 -0.1074 0.8435 0.0789
-5.000 -0.0427 0.02678 0.01938 -0.1067 0.8390 0.0805
-4.750 -0.0146 0.02555 0.01782 -0.1064 0.8358 0.0825
-4.500 0.0064 0.02499 0.01699 -0.1049 0.8305 0.0837
-4.250 0.0279 0.02352 0.01546 -0.1040 0.8248 0.0855
-4.000 0.0565 0.02268 0.01460 -0.1041 0.8210 0.0879
-3.750 0.0874 0.02196 0.01378 -0.1044 0.8180 0.0912
-3.500 0.1099 0.02161 0.01330 -0.1033 0.8124 0.0940
-3.250 0.1346 0.02082 0.01243 -0.1026 0.8067 0.0965
-3.000 0.1644 0.02007 0.01172 -0.1028 0.8029 0.1003
-2.750 0.1966 0.01949 0.01106 -0.1033 0.7997 0.1049
-2.500 0.2170 0.01938 0.01090 -0.1018 0.7926 0.1078
-2.250 0.2441 0.01857 0.01018 -0.1016 0.7874 0.1127
-2.000 0.2752 0.01805 0.00964 -0.1019 0.7835 0.1183
-1.750 0.3000 0.01781 0.00936 -0.1011 0.7776 0.1228
-1.500 0.3237 0.01730 0.00896 -0.1003 0.7711 0.1293
-1.250 0.3541 0.01686 0.00848 -0.1004 0.7665 0.1367
-1.000 0.3783 0.01648 0.00818 -0.0996 0.7605 0.1457
-0.750 0.4022 0.01618 0.00792 -0.0987 0.7533 0.1578
-0.500 0.4313 0.01559 0.00744 -0.0987 0.7483 0.1870
-0.250 0.4789 0.01350 0.00794 -0.1018 0.7420 0.8997
0.000 0.5624 0.01378 0.00804 -0.1119 0.7351 0.9748
0.250 0.6631 0.01343 0.00743 -0.1267 0.7293 1.0000
0.500 0.6838 0.01346 0.00743 -0.1254 0.7192 1.0000
0.750 0.7107 0.01333 0.00715 -0.1250 0.7118 1.0000
1.000 0.7314 0.01337 0.00715 -0.1237 0.7011 1.0000
1.250 0.7580 0.01328 0.00692 -0.1233 0.6931 1.0000
1.500 0.7783 0.01330 0.00693 -0.1218 0.6813 1.0000
1.750 0.8011 0.01329 0.00684 -0.1207 0.6705 1.0000
2.000 0.8250 0.01324 0.00667 -0.1198 0.6594 1.0000
2.250 0.8449 0.01327 0.00667 -0.1182 0.6454 1.0000
2.500 0.8656 0.01331 0.00665 -0.1168 0.6314 1.0000
2.750 0.8866 0.01336 0.00662 -0.1154 0.6174 1.0000
3.000 0.9075 0.01344 0.00660 -0.1140 0.6033 1.0000
3.250 0.9282 0.01356 0.00659 -0.1125 0.5895 1.0000
3.500 0.9481 0.01373 0.00665 -0.1110 0.5755 1.0000
3.750 0.9670 0.01395 0.00678 -0.1093 0.5619 1.0000
4.000 0.9862 0.01419 0.00693 -0.1077 0.5495 1.0000
4.250 1.0068 0.01447 0.00707 -0.1063 0.5388 1.0000
4.500 1.0253 0.01476 0.00730 -0.1046 0.5281 1.0000
4.750 1.0456 0.01507 0.00753 -0.1032 0.5191 1.0000
5.000 1.0650 0.01538 0.00778 -0.1017 0.5104 1.0000
5.250 1.0861 0.01572 0.00805 -0.1006 0.5028 1.0000
5.500 1.1043 0.01603 0.00835 -0.0989 0.4952 1.0000
5.750 1.1286 0.01640 0.00860 -0.0984 0.4884 1.0000
6.000 1.1428 0.01669 0.00895 -0.0959 0.4806 1.0000
6.250 1.1635 0.01702 0.00919 -0.0946 0.4731 1.0000
6.500 1.1785 0.01734 0.00954 -0.0923 0.4657 1.0000
6.750 1.1952 0.01764 0.00982 -0.0904 0.4587 1.0000
7.000 1.2173 0.01801 0.01012 -0.0895 0.4526 1.0000
7.250 1.2301 0.01831 0.01049 -0.0868 0.4463 1.0000
7.500 1.2483 0.01863 0.01079 -0.0851 0.4404 1.0000
7.750 1.2694 0.01901 0.01114 -0.0841 0.4348 1.0000
8.000 1.2810 0.01931 0.01152 -0.0812 0.4288 1.0000
8.250 1.2990 0.01963 0.01185 -0.0796 0.4234 1.0000
8.500 1.3226 0.02004 0.01220 -0.0791 0.4182 1.0000
8.750 1.3318 0.02036 0.01264 -0.0759 0.4124 1.0000
9.000 1.3477 0.02069 0.01299 -0.0740 0.4070 1.0000
9.250 1.3741 0.02111 0.01333 -0.0741 0.4017 1.0000
9.500 1.3794 0.02147 0.01384 -0.0702 0.3967 1.0000
9.750 1.3925 0.02184 0.01428 -0.0679 0.3914 1.0000
10.000 1.4139 0.02222 0.01462 -0.0671 0.3863 1.0000
10.250 1.4259 0.02269 0.01520 -0.0648 0.3812 1.0000
10.500 1.4357 0.02315 0.01576 -0.0621 0.3756 1.0000
10.750 1.4525 0.02355 0.01615 -0.0606 0.3699 1.0000
11.000 1.4633 0.02410 0.01679 -0.0583 0.3641 1.0000
11.250 1.4703 0.02469 0.01748 -0.0555 0.3575 1.0000
11.500 1.4863 0.02514 0.01787 -0.0541 0.3506 1.0000
11.750 1.4851 0.02599 0.01892 -0.0504 0.3430 1.0000
12.000 1.4945 0.02662 0.01950 -0.0483 0.3348 1.0000
12.250 1.4932 0.02771 0.02076 -0.0451 0.3259 1.0000
12.500 1.4983 0.02864 0.02167 -0.0427 0.3166 1.0000
12.750 1.4976 0.02994 0.02310 -0.0401 0.3059 1.0000
13.000 1.4990 0.03131 0.02453 -0.0378 0.2949 1.0000
13.250 1.4991 0.03283 0.02607 -0.0355 0.2830 1.0000
13.500 1.4973 0.03462 0.02786 -0.0334 0.2697 1.0000
13.750 1.4942 0.03667 0.02995 -0.0314 0.2550 1.0000
14.000 1.4900 0.03897 0.03223 -0.0295 0.2397 1.0000
14.250 1.4855 0.04144 0.03468 -0.0278 0.2252 1.0000
14.500 1.4816 0.04399 0.03722 -0.0263 0.2124 1.0000
14.750 1.4786 0.04654 0.03976 -0.0250 0.2021 1.0000
15.000 1.4745 0.04926 0.04244 -0.0238 0.1939 1.0000
15.250 1.4729 0.05185 0.04506 -0.0228 0.1863 1.0000
15.500 1.4699 0.05458 0.04776 -0.0218 0.1799 1.0000
15.750 1.4700 0.05714 0.05039 -0.0211 0.1737 1.0000
16.000 1.4675 0.05991 0.05312 -0.0204 0.1684 1.0000
16.250 1.4682 0.06252 0.05583 -0.0199 0.1632 1.0000
16.500 1.4668 0.06539 0.05875 -0.0196 0.1579 1.0000
16.750 1.4657 0.06808 0.06139 -0.0191 0.1530 1.0000
17.000 1.4645 0.07119 0.06469 -0.0191 0.1483 1.0000
17.250 1.4610 0.07450 0.06807 -0.0191 0.1431 1.0000
17.500 1.4581 0.07769 0.07127 -0.0192 0.1383 1.0000
17.750 1.4542 0.08134 0.07510 -0.0196 0.1332 1.0000
18.000 1.4483 0.08512 0.07891 -0.0201 0.1282 1.0000
18.250 1.4424 0.08908 0.08301 -0.0208 0.1227 1.0000
18.500 1.4333 0.09357 0.08760 -0.0217 0.1164 1.0000
18.750 1.4234 0.09827 0.09241 -0.0228 0.1092 1.0000
19.000 1.4093 0.10361 0.09778 -0.0243 0.1014 1.0000
19.250 1.3939 0.10926 0.10350 -0.0259 0.0913 1.0000
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